طراحی و تحلیل اجکتور سیال ثانویه در سکوی شبیه‌ساز ارتفاع

نوع مقاله : مقاله پژوهشی

نویسندگان

1 مهندسی هوافضا/ دانشگاه صنعتی امیرکبیر

2 گروه پژوهشی پیشران/پژوهشکده سامانه های حمل ونقل فضایی/ پژوهشگاه فضایی ایران، تهران/ایران

3 دانشکده مهندسی هوافضا/ دانشگاه صنعتی امیرکبیر

چکیده

غالبا" جهت تست زمینی موتورهای مورد استفاده در فضا از سکوی شبیه‌ساز ارتفاع استفاده می‌شود. این سکو  مجهز به یک دیفیوزر خروجی گاز مافوق صوت است. جریان گازهای احتراقی خروجی از موتور به طور خودکار از طریق دیفیوزر به محیط اتمسفر تخلیه شده و فشار پایین مطلوب در اطراف موتور برقرار می‌شود. در صورتی که فشار موتور از حدی پایین‌تر باشد، جریان مافوق صوت در دیفیوزر برقرار نمی‌شود. در این حالت نیاز است از اجکتور کمکی در انتهای دیفیوزر استفاده شود. در تحقیق حاضر، الگوریتم جدیدی در طراحی اجکتور مافوقصوت توسعه داده شده است. برخالف روش‌های رایج، الگوریتم مزبور قابلیت استفاده از سیال اولیه (ورودی از نازل اجکتور) و سیال ثانویه (خروجی از انتهای دیفیوزر)  مختلف را دارد. در طراحی اجکتور، پارامترهای اصلی توسط الگوریتم تعیین می‌شوند؛ در حالی که پارامترهای فرعی از نتایج تست تجربی مراجع معتبر و یا شبیه‌سازی عددی انتخاب می‌شوند. در الگوریتم طراحی، حاشیه اطمینان لازم برای کارکرد مطلوب اجکتور پیش‌بینی شده است که توسط شبیه‌سازی عددی جریان به دست می‌آید. همچنین از شبیه‌سازی عددی جریان برای تأیید روش طراحی استفاده می‌شود. در انتها با استفاده از الگوریتم ارائه شده، یک اجکتور برای کم کردن فشار استارت یک مجموعه موتور-دیفیوزر مافوق صوت، طراحی شده است. شبیه‌سازی یکپارچه دیفیوزر-اجکتور برای دو حالت موتور خاموش و موتور روشن انجام شده و مناسب بودن طراحی انجام شده برای اجکتور در هر دو حالت مورد تأیید قرار گرفته است.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Design and Analysis of Gas Ejector in High Altitude Test Facility

نویسندگان [English]

  • Esmail Mohammadi 1
  • Nematollah Fouladi 2
  • Ali Madadi 3
1 Aerospace Engineering/ Amirkabir University of Technology
2 Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran
3 Aerospace Engineering/ Amirkabir University of Technology
چکیده [English]

Usually, ground testing of space engines is performed in a high altitude test facility. The facility is equipped with a supersonic diffuser that expels automatically engine gases to the atmospheric environment and maintains a vacuum pressure around its nozzle and motor. Normally; in the case of lower motor pressure, the supersonic flow in the diffuser could not be established. In this situation, an auxiliary ejector is employed frequently at the end section of the diffuser. In the present study, a new algorithm for designing the supersonic ejector has been proposed. Unlike conventional methods, this algorithm can be used with different primary and secondary fluids. The main design parameters are determined by the algorithm, while the secondary parameters are selected from the experimental test results of the existing references. A safe margin is considered for the safe operation of the ejector, which is predicted through the numerical simulations. Also, numerical simulation is used to verify the present design algorithm. Finally, using the proposed algorithm, an ejector is designed to reduce the minimum starting pressure of a second throat exhaust diffuser. An integrated simulation of the diffuser-ejector is performed and the appropriateness of the designed ejector is confirmed.

کلیدواژه‌ها [English]

  • High Altitude Test Facility
  • Supersonic ejector
  • Design algorithm
  • numerical simulation
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